US 9,809,317 B2
Engine mount
Richard Geoffrey Stretton, Loughborough (GB); and Kenneth Franklin Udall, Ilkeston (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE PLC, London (GB)
Filed on Nov. 17, 2014, as Appl. No. 14/543,402.
Claims priority of application No. 1322077.7 (GB), filed on Dec. 13, 2013.
Prior Publication US 2016/0167797 A1, Jun. 16, 2016
Int. Cl. B64D 27/26 (2006.01); F02C 7/20 (2006.01); B64D 27/10 (2006.01)
CPC B64D 27/26 (2013.01) [B64D 27/10 (2013.01); F02C 7/20 (2013.01); B64D 2027/262 (2013.01); F05D 2220/325 (2013.01); F05D 2250/11 (2013.01)] 12 Claims
OG exemplary drawing
 
11. A gas turbine engine comprising:
a mounting system attaching the gas turbine engine to a pylon of an aircraft, the mounting system including:
a first frame of three elongate members arranged in a triangle, the first frame being arranged so that a core of the gas turbine engine is positioned extending through an area defined between the three elongate members of the first frame, the first frame being arranged so that the first frame forms at least part of a load bearing connection between the pylon and the gas turbine engine, the first frame consisting of two portions, each portion respectively corresponding to each side of the gas turbine engine as attached to the pylon at a location of the first frame, the triangle formed by the first frame being symmetrical about a first plane separating the two portions of the first frame; and
a second frame of three elongate members arranged in a triangle, the second frame being arranged so that the core of the gas turbine engine is positioned extending through an area defined between the three elongate members of the second frame, the second frame being arranged so that the second frame forms at least part of the load bearing connection between the pylon and the gas turbine engine, the second frame consisting of two portions, each portion respectively corresponding to each side of the gas turbine engine as attached to the pylon at a location of the second frame, the triangle formed by the second frame being symmetrical about a second plane separating the two portions of the second frame; wherein
the gas turbine engine is attached to the mounting system such that both of the first frame and the second frame are positioned axially forward of a radially extending projection of a first turbine stage in the core of the gas turbine engine.